AD 2008-06-10 Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes

This AD applies to Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category; as identified in Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Detailed Inspection (f) Before the accumulation of 8,600 total flight cycles, or within 1,100 flight cycles after the effective date of this AD, whichever occurs later: Perform a detailed inspection to detect cracking of the left side and right side frames and reinforcement angles at FS640 between stringer 9 and stringer 12, in accordance with Part A of the Accomplishment Instructions of Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006. Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” Repetitive Inspection and Corrective Action (g) If no crack is found during the inspection required by paragraph (f) of this AD: Repeat the detailed inspection thereafter at intervals not to exceed 1,100 flight cycles, until the frame modification described in paragraph (h)(2) of this AD or the optional terminating modification described in paragraph (i) of this AD has been done. (h) If any crack is found during the inspection required by paragraph (g) of this AD: Before further flight, repair the crack in accordance with paragraph (h)(1), (h)(2), or (h)(3) of this AD, as applicable. (1) For any crack found in the frame at the stringer 9 cut-out only, repair in accordance with Part A of the Accomplishment Instructions of Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006. (2) For any crack found in the frame reinforcement doubler only, do the actions described in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) Do the frame modification (including related investigative and corrective actions) described in Part C of the Accomplishment Instructions of Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006; except where the service bulletin specifies to contact the manufacturer for repair instructions, repair the crack using a method approved by either the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent). (ii) Within 12,000 flight cycles after doing the modification required by paragraph (h)(2)(i) of this AD, do the detailed inspection required by paragraph (f) of this AD, then repeat the detailed inspection thereafter at intervals not to exceed 1,100 flight cycles. (3) For any crack found in areas of the inspection zone described in paragraph (f) of this AD other than those areas described in paragraphs (h)(1) and (h)(2) of this AD: Repair the crack using a method approved by either the Manager, New York ACO, FAA; or TCCA (or its delegated agent). Optional Terminating Action (i) Reinforcement of any engine support beam in accordance with the Accomplishment Instructions of the service information described in paragraph (i)(1) or (i)(2) of this AD, as applicable, ends all repetitive inspections required by this AD for that support beam. (1) For all airplanes: If the reinforcement is done before the effective date of this AD, Bombardier Alert Service Bulletin A601R-53-059, Revision E, dated March 21, 2005; or Revision F, dated April 21, 2006; may be used. After the effective date of this AD, only Bombardier Alert Service Bulletin A601R-53-059, Revision F, may be used. (2) For airplanes identified in Bombardier Service Bulletin 601R-53-065, Revision B, dated November 2, 2007: If the reinforcement is done before the effective date of this AD, Bombardier Service Bulletin 601R-53-065, Revision A, dated August 24, 2005, or Revision B, may be used. After the effective date of this AD, only Bombardier Service Bulletin 601R-53-065, Revision B, may be used. No Reporting Requirement (j) Although Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006, specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, New York ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (l) Canadian airworthiness directive CF-2003-12, dated May 7, 2003, also addresses the subject of this AD. Material Incorporated by Reference (m) You must use Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006, including Appendix B, Revision C, dated June 25, 2003, to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the optional actions specified by this AD, you must use Bombardier Alert Service Bulletin A601R-53-059, Revision F, dated April 21, 2006, excluding Appendix A, dated June 14, 2001; or Bombardier Service Bulletin 601R-53-065, Revision B, dated November 2, 2007; as applicable; to perform those actions, unless the AD specifies otherwise. Bombardier Service Bulletin 601R-53-061, Revision E, dated December 7, 2006, includes the following effective pages:   Page Nos. Revision level shown on page Date shown on page 1-44 E December 7, 2006. Appendix B B1-B8 C June 25, 2003. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada. (3) You may review copies of the service information incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . Issued in Renton, Washington, on March 3, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-4644 Filed 3-11-08; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports that cracks have been discovered on the frame and reinforcement angles at fuselage station (FS) 640. Failure of this frame could degrade the structural integrity of the airplane. We are issuing this AD to detect and correct cracking of the frame, which could lead to failure of the fuselage structure and possible loss of the airplane.